* lib: add FilteredDerivative class
* AirspeedValidator: add first principle check
- filters throttle, pitch and airspeed rate, and triggers
if the airspeed rate is negative even though the vehicle
is pitching down and giving high throttle.
Check has to fail for duration defined by ASPD_FP_T_WINDOW
to trigger an airspeed failure.
* AirspeedValidator: define constants for first principle check
* FilteredDerivative: set initialised to false if sample interval is invalid
* airspeed_selector: improved comment
* increase IAS derivative filter time constant from 4 to 5
* use legacy parameter handling for FW_PSP_OFF
* handle FW_THR_MAX as well
* ROMFS/airframes: exclude some airframes for v6x and v4pro to save flash on them
---------
Signed-off-by: Silvan Fuhrer <silvan@auterion.com>
Signed-off-by: RomanBapst <bapstroman@gmail.com>
Co-authored-by: Silvan Fuhrer <silvan@auterion.com>
Pulls cell count, min voltage and max voltage from log file but still allows for over-rides. Also added debug info to tell user what what it found in the log and what it is using
Co-authored-by: chfriedrich98 <125505139+chfriedrich98@users.noreply.github.com>
- MPC_VEL_LP: new velocity first order low pass filter (off by default)
- MPC_VEL_NF_FRQ/MPC_VEL_NF_BW: new velocity notch filter (off by default)
- MPC_VELD_LP: existing velocity derivative low pass filter, but I've dropped the remaining controllib usage
The case where the airframe maintainer wants to enforce a reset to airframe is
not covered anymore with the `param set-default` mechanism. For products based
on PX4 this is still required to ensure proper functionality after a major update.
VTOLs consume a lot more power in hover copared to fixed-wing fligt.
The remaining flight time thus should reset if one switches from MC to FW,
as otherwise it takes several minutes until the estimate goes down.
- upate to NOAA grid API to build WMM table in one pass
- refactor declination/inclination/totalintensity table printing to
shared method
- compute scaling factor to maximize resolution
- warn about full traffic conflict buffer at 1/60hz.
- add conflict expiry for buffer.
- use only events for buffer full warning. mavlink_log_critical no longer needed.
- use icao address for conflict warnings id, stop using uas_id. UTM_GLOBAL_POSITION assumed deprecated.
- stop spamming when buffer is full
- fix warning wording if buffer is full.
- remove UTM_GLOBAL_POSITION
Fixes failing unit test:
* [adsbTest] Reduce conflict timestamps - not enough time has passed in ci
- failed ci output - (passes locally with make tests TESTFILTER=AdsbConflict)
- Timestamp: 6000000000
- Time now: 457720038
- Time since timestamp: 0
- Old Conflict warning expired: 0
- --------------------
- adsb_conflict._traffic_state 0
- ../../src/lib/adsb/AdsbConflictTest.cpp:244: Failure
- Value of: adsb_conflict._traffic_state == TRAFFIC_STATE::REMIND_CONFLICT
- Actual: false
- Expected: true
This is a minimal change to make it harder to crash a
vehicle with an empty battery if the capacity was set wrong.
The disadvantage is that the state of charge estimate will
fluctuate more under load.
We need better documentation and improvements to the estimation.
- Added an empty constructor, setPort, and validatePort functions for Serial API
- Changed GPS to not allocate Serial object dynamically
- Moved access check on serial port name into the Serial API
- Improved the Qurt platform validatePort Serial function to implement a more rigorous check. Added safety check
to the setPort Serial function to make sure it isn't called after the port has been already opened.
This matters for PWM when the last output gets disabled on either FMU or IO
it would just keep on running.
Also when rebooting with a parameters reset or new airframe with no mapped outputs
it would previously keep outputting PWM with the disarmed value of the new airframe
e.g. 1000us which is a safety hazard because servos could break the physical limit of the
model or miscalibrated ESCs spinning motors.
